以5种不同弯度的弧形翼为研究对象,通过风洞实验方法,采用同步测压技术,建立弧形翼附面层压力场测试实验装置,测定5°~30°范围内典型来流攻角下叶片表面压力分布,分析翼型弯度对叶片升力的影响,研究弧形翼在低速运行时的气动性能。同时采用PIV技术,获取弧形翼附面层速度场。揭示低速时弧形翼模面层的流动分离和旋涡运动的规律,并探究弯度对弧形翼附面层流动转捩和分离的影响。 Five kinds of camber arcs with different camber as the research object, through the wind tunnel experiment method, the synchronous pressure measurement technology, the establishment of curved wing attached surface pressure field test device, measuring 5 ° ~ 30 ° range to the typical flow to attack The pressure distribution on the blade surface and the influence of the airfoil curvature on the blade lift are analyzed. The aerodynamic performance of arc wing at low speed is studied. At the same time using PIV technology, access to arc wing attached layer velocity field. The law of flow separation and vortex motion of curved wing mold surface layer was revealed at low speed, and the effect of camber on the flow transition and separation of arc wing lamina was also investigated.